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Home > Forums > Aeronautic Engineers > Activities > Aircraft engineering Forum

wing load distributionHelpful Member! 

thread2-309889
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shearlag (Aeronautics)
4 Nov 11 12:00
Dear Readers,

If chordwise & spanwise CP distribution is known, nodal load can be evaluated on each node on the Fe model. If forces & moments are known at few locations (say 15 locations) on wing surface, what is proper way to distribute the load so that shear force, bending moment & torque diagram are same when done with Cp distribution.

thanks in advance
shearlag
Helpful Member!  rb1957 (Aerospace)
4 Nov 11 16:45
it sounds like you have a few data points, which you want to distribute onto a fine grid.

i'd start with a standard wing spanwise load distribution, schrenk, which'll give you shear force and bending moment.  tweek again to match your data.
shearlag (Aeronautics)
5 Nov 11 13:01
Yes rb1957, you got it right. i have few data points which i need to distribute on a fine grid.So you mean to say it can be done in a iterative way to match the shear force, bending moment & torque diagram.But various assumed distribution can give same max shear force, max bending moment & max torque moment at the root. Am I right in saying so..?

shearlag
rb1957 (Aerospace)
7 Nov 11 6:28
yes, so start with a "known"/typical/accepted spanwise distribution
shearlag (Aeronautics)
7 Nov 11 12:39
Thanks RB
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